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EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1098 AIRFOIL (e1098-il)
Reynolds number: 50,000
Max Cl/Cd: 5.3 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1098-il-50000.txt
Download as CSV file: xf-e1098-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1098 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5043   0.11647   0.11141  -0.0420   0.9897   0.1558
  -9.000  -0.5625   0.10621   0.10124  -0.0456   0.9927   0.1337
  -8.750  -0.5989   0.10246   0.09758  -0.0426   0.9969   0.1303
  -8.500  -0.6485   0.09816   0.09333  -0.0404   1.0000   0.1289
  -8.250  -0.6993   0.09388   0.08904  -0.0393   1.0000   0.1279
  -8.000  -0.7531   0.08825   0.08319  -0.0395   1.0000   0.1257
  -7.750  -0.7745   0.08323   0.07788  -0.0392   1.0000   0.1200
  -7.500  -0.7832   0.07840   0.07283  -0.0386   1.0000   0.1157
  -7.250  -0.8042   0.07223   0.06562  -0.0392   1.0000   0.1078
  -7.000  -0.7949   0.06823   0.06153  -0.0385   1.0000   0.1055
  -6.750  -0.7870   0.06422   0.05716  -0.0381   1.0000   0.1029
  -6.500  -0.7760   0.06047   0.05293  -0.0379   1.0000   0.1005
  -6.250  -0.7619   0.05731   0.04931  -0.0375   1.0000   0.1001
  -6.000  -0.7456   0.05468   0.04629  -0.0371   1.0000   0.1013
  -5.750  -0.7274   0.05237   0.04359  -0.0366   1.0000   0.1027
  -5.500  -0.7077   0.05024   0.04108  -0.0359   1.0000   0.1041
  -5.250  -0.6873   0.04845   0.03896  -0.0350   1.0000   0.1052
  -5.000  -0.6664   0.04698   0.03715  -0.0338   1.0000   0.1071
  -4.750  -0.6471   0.04562   0.03581  -0.0321   1.0000   0.1113
  -4.500  -0.6286   0.04474   0.03497  -0.0304   1.0000   0.1190
  -4.250  -0.6110   0.04398   0.03426  -0.0281   1.0000   0.1264
  -4.000  -0.5935   0.04334   0.03357  -0.0261   1.0000   0.1373
  -3.750  -0.5774   0.04225   0.03276  -0.0247   1.0000   0.1556
  -3.500  -0.5573   0.04043   0.03136  -0.0250   1.0000   0.1971
  -3.250  -0.5600   0.04225   0.03581  -0.0146   1.0000   0.5925
  -3.000  -0.5654   0.04525   0.03877  -0.0030   1.0000   0.6402
  -2.750  -0.5675   0.04710   0.04055   0.0065   1.0000   0.6730
  -2.500  -0.5718   0.04863   0.04203   0.0165   1.0000   0.7066
  -2.250  -0.5804   0.05000   0.04339   0.0280   1.0000   0.7486
  -2.000  -0.5881   0.05102   0.04437   0.0395   1.0000   0.7926
  -1.750  -0.5790   0.05209   0.04529   0.0480   1.0000   0.8336
  -1.500  -0.5660   0.05177   0.04474   0.0499   1.0000   0.8515
  -1.250  -0.5475   0.05140   0.04413   0.0502   1.0000   0.8620
  -1.000  -0.5381   0.05063   0.04316   0.0512   1.0000   0.8706
  -0.750  -0.5198   0.05027   0.04260   0.0509   1.0000   0.8779
  -0.500  -0.5093   0.04961   0.04174   0.0515   1.0000   0.8847
  -0.250  -0.4888   0.04942   0.04136   0.0506   1.0000   0.8904
   0.000  -0.4736   0.04906   0.04083   0.0503   1.0000   0.8962
   0.250  -0.4568   0.04882   0.04042   0.0498   1.0000   0.9011
   0.500  -0.4370   0.04876   0.04021   0.0488   1.0000   0.9059
   0.750  -0.4193   0.04869   0.03998   0.0480   1.0000   0.9109
   1.000  -0.3999   0.04874   0.03989   0.0468   1.0000   0.9152
   1.250  -0.3777   0.04899   0.04002   0.0452   1.0000   0.9198
   1.500  -0.3566   0.04927   0.04017   0.0437   1.0000   0.9247
   1.750  -0.3298   0.05000   0.04077   0.0410   0.9973   0.9292
   2.000  -0.2935   0.05142   0.04207   0.0364   0.9906   0.9338
   2.250  -0.2539   0.05347   0.04399   0.0312   0.9832   0.9395
   2.500  -0.2225   0.05437   0.04480   0.0275   0.9736   0.9440
   2.750  -0.1880   0.05570   0.04605   0.0232   0.9646   0.9487
   3.000  -0.1449   0.05821   0.04848   0.0172   0.9566   0.9555
   3.250  -0.1108   0.05921   0.04943   0.0130   0.9450   0.9607
   3.500  -0.0780   0.06045   0.05065   0.0089   0.9340   0.9666
   3.750  -0.0400   0.06242   0.05258   0.0037   0.9250   0.9730
   4.000   0.0045   0.06487   0.05500  -0.0027   0.9137   0.9813
   4.250   0.0317   0.06567   0.05581  -0.0058   0.9005   0.9916
   4.500   0.0488   0.06639   0.05652  -0.0071   0.8888   1.0000
   4.750   0.0713   0.06788   0.05797  -0.0094   0.8791   1.0000
   5.000   0.1024   0.06993   0.06000  -0.0132   0.8680   1.0000
   5.250   0.1212   0.07080   0.06086  -0.0149   0.8554   1.0000
   5.500   0.1442   0.07237   0.06243  -0.0174   0.8447   1.0000
   5.750   0.1887   0.07619   0.06622  -0.0236   0.8360   1.0000
   6.000   0.2069   0.07702   0.06708  -0.0253   0.8226   1.0000
   6.250   0.2272   0.07850   0.06858  -0.0274   0.8102   1.0000
   6.500   0.2514   0.08062   0.07072  -0.0303   0.7994   1.0000
   6.750   0.2972   0.08478   0.07489  -0.0363   0.7898   1.0000
   7.000   0.3135   0.08593   0.07608  -0.0378   0.7761   1.0000
   7.250   0.3311   0.08761   0.07780  -0.0397   0.7631   1.0000
   7.500   0.3511   0.08980   0.08004  -0.0419   0.7514   1.0000
   7.750   0.3796   0.09283   0.08309  -0.0453   0.7412   1.0000
   8.000   0.4156   0.09626   0.08656  -0.0493   0.7287   1.0000
   8.250   0.4271   0.09774   0.08809  -0.0502   0.7152   1.0000
   8.500   0.4403   0.09976   0.09017  -0.0515   0.7027   1.0000
   8.750   0.4572   0.10227   0.09272  -0.0532   0.6914   1.0000
   9.000   0.4847   0.10559   0.09609  -0.0559   0.6809   1.0000
   9.250   0.5135   0.10871   0.09926  -0.0584   0.6677   1.0000
   9.500   0.5180   0.11025   0.10087  -0.0586   0.6548   1.0000
   9.750   0.5263   0.11254   0.10322  -0.0593   0.6438   1.0000
  10.000   0.5447   0.11556   0.10630  -0.0609   0.6339   1.0000
  10.250   0.5735   0.11899   0.10980  -0.0631   0.6216   1.0000
  10.500   0.5841   0.12105   0.11194  -0.0638   0.6085   1.0000
  10.750   0.5844   0.12323   0.11420  -0.0641   0.5986   1.0000
  11.250   0.6614   0.12477   0.11591  -0.0652   0.5336   1.0000
  11.500   0.6670   0.12900   0.12024  -0.0668   0.5341   1.0000
  11.750   0.6402   0.13425   0.12556  -0.0685   0.5523   1.0000
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